US8572985B2 - Air filtration system for gas turbine engine pneumatic system - Google Patents

Air filtration system for gas turbine engine pneumatic system Download PDF

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Publication number
US8572985B2
US8572985B2 US12/492,214 US49221409A US8572985B2 US 8572985 B2 US8572985 B2 US 8572985B2 US 49221409 A US49221409 A US 49221409A US 8572985 B2 US8572985 B2 US 8572985B2
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US
United States
Prior art keywords
air
passage
pneumatic system
bleed valve
wash filter
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Fee Related, expires
Application number
US12/492,214
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English (en)
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US20100326090A1 (en
Inventor
David Waddleton
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Pratt and Whitney Canada Corp
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Pratt and Whitney Canada Corp
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Priority to US12/492,214 priority Critical patent/US8572985B2/en
Assigned to PRATT & WHITNEY CANADA CORP. reassignment PRATT & WHITNEY CANADA CORP. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: WADDLETON, DAVID
Priority to CA2706211A priority patent/CA2706211C/fr
Publication of US20100326090A1 publication Critical patent/US20100326090A1/en
Application granted granted Critical
Publication of US8572985B2 publication Critical patent/US8572985B2/en
Expired - Fee Related legal-status Critical Current
Adjusted expiration legal-status Critical

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/06—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas
    • F02C6/08—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output providing compressed gas the gas being bled from the gas-turbine compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/18—Control of working fluid flow by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/60—Fluid transfer
    • F05D2260/607—Preventing clogging or obstruction of flow paths by dirt, dust, or foreign particles

Definitions

  • the described subject matter relates generally to gas turbine engines and more particularly, to an improved gas turbine engine pneumatic system including an air filtration system.
  • FIG. 4 An example of a gas turbine engine pneumatic system for controlling the open/closed condition of an air bleed valve is schematically shown in FIG. 4 in which a pressure Px is applied to one side of a poppet valve against the high pressure P 0 of compressed air acting on the other side of the poppet valve.
  • the Px pressure is generated for example, by a simple dropping orifice network flowing air between a high pressure air source and a low pressure sink which is usually the ambient air pressure.
  • the arrangement in conjunction with the reference spring (not numbered), provides for a predetermined relationship between the valve open/closed positions and the pressure Px which in turn is based on the geometric features. For some gas turbine engine installations, it is necessary to adjust this relationship to provide additional engine operational flexibility, particularly during transient maneuvers. Accordingly, there is a need to provide an improved gas turbine engine pneumatic system for controlling an air bleed valve.
  • a gas turbine engine pneumatic system for controlling an air bleed valve comprising: an apparatus for generating a maximum air pressure; a first passage extending between the apparatus and the air bleed valve for applying the maximum air pressure to the air bleed valve to close the air bleed valve against a pressure of pressurized air; a second passage connected to the first passage and a variable orifice device included in the second passage to controllably discharge air from the first passage through the variable orifice device, thereby reducing the maximum air pressure applied to the air bleed valve to a predetermined level; and a filter device located in the pneumatic system for filtering the air discharged through the variable orifice device.
  • a gas turbine engine comprising: an air bleed valve for selectively bleeding air from a contained pressurized air; a pneumatic system for applying a maximum air pressure to the air bleed valve to close the air bleed valve against a pressure of the pressurized air; wherein the pneumatic system comprises a variable orifice device for controllably discharging air from the pneumatic system through the variable orifice device, thereby reducing the maximum air pressure applied to the air bleed valve to a predetermined level; and wherein the pneumatic system comprises means for filtering the air discharged through the variable orifice device.
  • FIG. 1 is a schematic cross-sectional view of a turbofan gas turbine engine as an exemplary application of the described subject matter
  • FIG. 2 is a schematic illustration of a gas turbine engine pneumatic system for controlling an air bleed valve according to one embodiment
  • FIG. 3 is a schematic illustration of a gas turbine engine pneumatic system for controlling an air bleed valve according to another embodiment.
  • FIG. 4 is a schematic illustration of a prior art gas turbine engine pneumatic system for controlling an air bleed valve.
  • a turbofan gas turbine engine presented as an example of the application of the described subject matter, includes a housing or nacelle 10 , a core casing 13 , a low pressure spool assembly which includes a fan assembly 14 , a low pressure compressor assembly 16 and a low pressure turbine assembly 18 , and a high pressure spool assembly which includes a high pressure compressor assembly 22 and a high pressure turbine assembly 24 .
  • a combustor 28 to constitute a gas generator section 26 .
  • a gas turbine engine pneumatic system generally indicated by numeral 30 for controlling an air bleed valve 32 such as a poppet valve which is a valve having a hole (not shown), usually round or oval and a tapered plug (not shown), usually a disk shape on the end of a shaft (also called a valve stem) (not shown).
  • the shaft guides the plug portion by sliding through a valve guide (not shown).
  • a pressure differential helps to seal the valve and in some applications also opens the valve.
  • the air bleed valve 32 is used under a maximum air pressure Px to seal an air bleed passage 34 to prevent air bleeding from a pressurized air system 36 to the air bleed passage 34 .
  • Po indicates the air pressure of the pressurized air system 36 , acting on the air bleed valve 32 .
  • the open/closed positions of the air bleed valve 32 are determined by forces acting on the opposite ends of the air bleed valve 32 which relate to the respective air pressures Po, Px (acting on the opposite ends of the valve) and the affected areas on which the respective air pressures Po, Px, act. Additional spring forces if any spring device is provided within the air bleed valve 32 , may also act on the valve. Therefore, changes in Po/Px pressure relationship may cause position changes of the air bleed valve 32 between the open and closed positions. Therefore, controlling the air bleed valve 32 may be achieved by adjusting the maximum air pressure Px with respect to the air pressure Po of the pressurized air.
  • the pneumatic system 30 may be presented, for example, as a simple orifice network in which a main air passage 38 is in fluid communication with a high pressure air source 40 at an upstream end of the pneumatic system 30 , and with a low pressure sink 42 which may actually be presented by ambient air pressure at a downstream end of the pneumatic system.
  • Orifices 44 , 46 represent fluid flow resistances existing in respective upstream and downstream sections of the main air passage 38 , but do not necessarily represent the physical confirmation or components of the orifice network. Therefore, a dropping orifice network air flow (not shown) passing through the main air passage 38 between the orifices 44 and 46 , will generate the maximum air pressure Px.
  • the fluid flow resistances represented by the orifices 44 , 46 are determined by the nature of the physical configuration of the main air passage 38 .
  • the maximum air pressure Px is determined by the fluid flow resistance represented by the orifices 44 and 46 , and is not adjustable once the physical configuration of the main air passage 38 is determined.
  • a further air passage 50 which includes a variable orifice device 52 , is connected to the air passage 48 for controllably discharging air from the air passage 48 through the variable orifice device 52 into a location 54 , for example with ambient air. This reduces the maximum air pressure Px applied to the air bleed valve 32 to a predetermined level, thereby adjusting the maximum air pressure Px and thus controlling the open/closed threshold of the bleed valve 32 .
  • a filter device such as a full-flow filter 56 may be installed in the air passage 48 at a location upstream of a point where the air passage 50 is connected to the air passage 48 . Therefore, the entire air flow which passes through the air passage 48 and the full-flow filter 56 and then through the air passage 50 and the variable orifice device 52 , is fully filtered by the full-flow filter 56 to prevent small gaps and fine holes in the variable orifice device 52 from being blocked or damaged by debris or particles carried by the air flow passing through the variable orfice device 52 .
  • the full-flow filter 56 may require periodic cleaning or replacement at intervals depending upon the operating environment of the engine.
  • variable orifice device 52 may be controlled by the engine control system such as the engine electric controller (EEC) 58 .
  • EEC engine electric controller
  • a gas turbine engine pneumatic system 30 ′ is provided for controlling the open/closed condition of the air bleed valve 32 according to another embodiment alternative to the gas turbine engine pneumatic system 30 of FIG. 2 .
  • Components and features of the alternative embodiment shown in FIG. 3 which are similar to those of FIG. 2 and are indicated by similar numerals will not be redundantly described.
  • a wash filter 60 may be installed in the main air passage 38 at a location between the orifices 44 , 46 and connected to air passage 48 .
  • the wash filter 60 may be configured with a cylinder (not numbered) having an inlet 62 and an outlet 64 defined at opposed ends of the cylinder.
  • a layer of filtering medium 66 may be provided within the cylinder and attached to the entire cylindrical inner surface of the cylinder in order to define an axial passage 68 extending between the inlet 62 and outlet 64 , thereby allowing a first portion of an air flow which enters the inlet 62 of the wash filter 60 , to pass through the axial passage 68 and to be discharged out of the wash filter 60 through the outlet 64 without filtration.
  • a side outlet 70 connected to the air passage 48 may be defined in the sidewall of the cylinder in order to allow a second portion of the air flow which enters the inlet 62 of the wash filter 60 , to pass through the filtering medium 66 and to then be discharged out of the wash filter 60 through the side outlet 70 into the air passage 48 , thereby generating the maximum air pressure Px.
  • the air flow which passes through air passage 48 and air passage 50 and the variable orfice device 52 is fully filtered by the wash filter 60 .
  • the wash filter 60 in contrast to the full-flow filter 56 in FIG. 2 , may require less cleaning and filter replacement, thereby significantly extending filter maintenance intervals because the air flow required for the dropping orifice network (through the main air passage 38 ) passes through the axial passage 68 of the wash filter 60 and thus washes the filtering medium 66 , thereby carrying debris and particles trapped in the filtering medium 66 away from the wash filter 60 .
  • full-flow filter 56 of FIG. 2 is known in the art and the specific configuration thereof is not described in detail. Full-flow filters of various types may be applicable for the gas turbine engine pneumatic system as described with reference to FIG. 2 . It should also be noted that wash filters are known in the art and wash filters of various types different from the described wash filter 60 of FIG. 3 , may be used for the pneumatic system described with reference to FIG. 3 .

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Turbines (AREA)
US12/492,214 2009-06-26 2009-06-26 Air filtration system for gas turbine engine pneumatic system Expired - Fee Related US8572985B2 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US12/492,214 US8572985B2 (en) 2009-06-26 2009-06-26 Air filtration system for gas turbine engine pneumatic system
CA2706211A CA2706211C (fr) 2009-06-26 2010-06-04 Dispositif de filtration d'air pour systeme pneumatique de turbine a gaz

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Application Number Priority Date Filing Date Title
US12/492,214 US8572985B2 (en) 2009-06-26 2009-06-26 Air filtration system for gas turbine engine pneumatic system

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US8572985B2 true US8572985B2 (en) 2013-11-05

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Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107035536A (zh) * 2017-06-02 2017-08-11 中国航发南方工业有限公司 放气活门辅助装置及具有其的航空发动机
US9849992B2 (en) 2016-05-23 2017-12-26 United Technologies Corporation Inline pressure regulating valve assembly with inlet pressure bias
US10241523B2 (en) 2016-07-13 2019-03-26 Ge Aviation Systems, Llc Differential pressure regulating shut-off valve
US10273884B2 (en) 2016-06-09 2019-04-30 Hamilton Sundstrand Corporation Altitude compensating bleed valve
US10384786B2 (en) 2016-02-05 2019-08-20 United Technologies Corporation Thermally biased valve and anti-icing system
US10450955B2 (en) 2016-07-06 2019-10-22 United Technologies Corporation Nacelle anti ice system
US11022041B2 (en) 2015-10-13 2021-06-01 Raytheon Technologies Corporation Sensor snubber block for a gas turbine engine
EP4108896A2 (fr) 2021-06-25 2022-12-28 Pratt & Whitney Canada Corp. Système de filtration d'air et procédé pour soupape de purge de compresseur
EP4124739A1 (fr) 2021-07-30 2023-02-01 Pratt & Whitney Canada Corp. Bloc d'orifice pour soupape de purge de compresseur
US11639689B2 (en) 2021-09-17 2023-05-02 Pratt & Whitney Canada Corp. Intake device for gas turbine engine
US20230358171A1 (en) * 2022-05-06 2023-11-09 Pratt & Whitney Canada Corp. Apparatus for removing particulate matter from bleed gas and gas turbine engine including same

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3057244B1 (fr) * 2016-10-12 2020-06-12 Safran Aircraft Engines Dispositif ameliore de ventilation de turbomachine
CN106362527A (zh) * 2016-10-24 2017-02-01 广州达意隆包装机械股份有限公司 一种无菌气过滤系统

Citations (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158449A (en) 1976-12-07 1979-06-19 Pall Corporation Inlet air cleaner assembly for turbine engines
US4245462A (en) 1978-11-29 1981-01-20 The Bendix Corporation Starting system for a turbine engine
US4649950A (en) 1985-11-27 1987-03-17 Ex-Cell-O Corporation Fuel nozzle assembly with integral valve assembly and inlet wash filter and primary fuel take-off
US5116362A (en) 1990-12-03 1992-05-26 United Technologies Corporation Fuel metering and actuation system
US5315818A (en) 1992-02-21 1994-05-31 Lucas Industries Public Limited Company Fuel control system
US5339636A (en) 1992-12-04 1994-08-23 United Technologies Corporation Fuel splitter valve assembly for gas turbine
US5477673A (en) * 1994-08-10 1995-12-26 Pratt & Whitney Canada Inc. Handling bleed valve
US5517821A (en) 1993-12-10 1996-05-21 Columbus Mckinnon Corporation Pneumatic control circuit for applying constant force
US5715674A (en) 1995-12-22 1998-02-10 United Technologies Corporation Hydromechanical control for a variable delivery, positive displacement fuel pump
US5795998A (en) 1995-12-12 1998-08-18 Lucas Industries Public Limited Company Flow sensor and fuel control system
US5918458A (en) 1997-02-14 1999-07-06 General Electric Company System and method of providing clean filtered cooling air to a hot portion of a gas turbine engine
US6102001A (en) 1998-12-04 2000-08-15 Woodward Governor Company Variable displacement pump fuel metering system and electrohydraulic servo-valve for controlling the same
US6217280B1 (en) 1995-10-07 2001-04-17 Siemens Westinghouse Power Corporation Turbine inter-disk cavity cooling air compressor
US6393826B1 (en) 2000-02-25 2002-05-28 Hitachi, Ltd. Gas turbine
US6792762B1 (en) 1999-11-10 2004-09-21 Hitachi, Ltd. Gas turbine equipment and gas turbine cooling method
US6813876B2 (en) 2002-03-15 2004-11-09 Goodrich Control Systems Ltd. Fuel system
US6901761B1 (en) 2004-02-24 2005-06-07 General Electric Company System and method for regulating pressure of pilot air to combustor of gas turbine
US6990815B2 (en) 2001-08-29 2006-01-31 Hitachi, Ltd. Gas turbine and gas turbine high temperature section cooling method
US7104282B2 (en) 2003-08-26 2006-09-12 Honeywell International, Inc. Two stage solenoid control valve
US7204076B2 (en) 2003-07-25 2007-04-17 Goodrich Control Systems Ltd. Engine fuel control
US20070119146A1 (en) 2005-11-30 2007-05-31 Caterpillar Inc. Retarding and filter cleaning method and system
US7237386B2 (en) 2001-11-02 2007-07-03 Alstom Technology Ltd Process for controlling the cooling air mass flow of a gas turbine set
US7252068B2 (en) 2004-08-02 2007-08-07 Honeywell International, Inc. System and method to reduce fuel system pumping heat input
US7837753B2 (en) * 2007-11-30 2010-11-23 Honeywell International Inc. Systems for filtering particles from an airflow

Patent Citations (26)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4158449A (en) 1976-12-07 1979-06-19 Pall Corporation Inlet air cleaner assembly for turbine engines
US4245462A (en) 1978-11-29 1981-01-20 The Bendix Corporation Starting system for a turbine engine
US4649950A (en) 1985-11-27 1987-03-17 Ex-Cell-O Corporation Fuel nozzle assembly with integral valve assembly and inlet wash filter and primary fuel take-off
US5116362A (en) 1990-12-03 1992-05-26 United Technologies Corporation Fuel metering and actuation system
US5315818A (en) 1992-02-21 1994-05-31 Lucas Industries Public Limited Company Fuel control system
US5339636A (en) 1992-12-04 1994-08-23 United Technologies Corporation Fuel splitter valve assembly for gas turbine
US5517821A (en) 1993-12-10 1996-05-21 Columbus Mckinnon Corporation Pneumatic control circuit for applying constant force
US5477673A (en) * 1994-08-10 1995-12-26 Pratt & Whitney Canada Inc. Handling bleed valve
US6217280B1 (en) 1995-10-07 2001-04-17 Siemens Westinghouse Power Corporation Turbine inter-disk cavity cooling air compressor
US5795998A (en) 1995-12-12 1998-08-18 Lucas Industries Public Limited Company Flow sensor and fuel control system
US5715674A (en) 1995-12-22 1998-02-10 United Technologies Corporation Hydromechanical control for a variable delivery, positive displacement fuel pump
US5918458A (en) 1997-02-14 1999-07-06 General Electric Company System and method of providing clean filtered cooling air to a hot portion of a gas turbine engine
US6102001A (en) 1998-12-04 2000-08-15 Woodward Governor Company Variable displacement pump fuel metering system and electrohydraulic servo-valve for controlling the same
US6792762B1 (en) 1999-11-10 2004-09-21 Hitachi, Ltd. Gas turbine equipment and gas turbine cooling method
US6393826B1 (en) 2000-02-25 2002-05-28 Hitachi, Ltd. Gas turbine
US6769259B2 (en) 2000-02-25 2004-08-03 Hitachi, Ltd. Gas turbine having a cooling air system and a spray air system
US6990815B2 (en) 2001-08-29 2006-01-31 Hitachi, Ltd. Gas turbine and gas turbine high temperature section cooling method
US7237386B2 (en) 2001-11-02 2007-07-03 Alstom Technology Ltd Process for controlling the cooling air mass flow of a gas turbine set
US6813876B2 (en) 2002-03-15 2004-11-09 Goodrich Control Systems Ltd. Fuel system
US7204076B2 (en) 2003-07-25 2007-04-17 Goodrich Control Systems Ltd. Engine fuel control
US7104282B2 (en) 2003-08-26 2006-09-12 Honeywell International, Inc. Two stage solenoid control valve
US6907738B1 (en) 2004-02-24 2005-06-21 General Electric Company Pilot air apparatus and method for a combustor of gas turbine
US6901761B1 (en) 2004-02-24 2005-06-07 General Electric Company System and method for regulating pressure of pilot air to combustor of gas turbine
US7252068B2 (en) 2004-08-02 2007-08-07 Honeywell International, Inc. System and method to reduce fuel system pumping heat input
US20070119146A1 (en) 2005-11-30 2007-05-31 Caterpillar Inc. Retarding and filter cleaning method and system
US7837753B2 (en) * 2007-11-30 2010-11-23 Honeywell International Inc. Systems for filtering particles from an airflow

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11022041B2 (en) 2015-10-13 2021-06-01 Raytheon Technologies Corporation Sensor snubber block for a gas turbine engine
US10384786B2 (en) 2016-02-05 2019-08-20 United Technologies Corporation Thermally biased valve and anti-icing system
US9849992B2 (en) 2016-05-23 2017-12-26 United Technologies Corporation Inline pressure regulating valve assembly with inlet pressure bias
US10273884B2 (en) 2016-06-09 2019-04-30 Hamilton Sundstrand Corporation Altitude compensating bleed valve
US10450955B2 (en) 2016-07-06 2019-10-22 United Technologies Corporation Nacelle anti ice system
US11060454B2 (en) 2016-07-06 2021-07-13 Raytheon Technologies Corporation Method of regulating air pressure in anti-icing system
US10241523B2 (en) 2016-07-13 2019-03-26 Ge Aviation Systems, Llc Differential pressure regulating shut-off valve
CN107035536A (zh) * 2017-06-02 2017-08-11 中国航发南方工业有限公司 放气活门辅助装置及具有其的航空发动机
EP4108896A2 (fr) 2021-06-25 2022-12-28 Pratt & Whitney Canada Corp. Système de filtration d'air et procédé pour soupape de purge de compresseur
US11802509B2 (en) 2021-06-25 2023-10-31 Pratt & Whitney Canada Corp. Air filtration system and method for compressor bleed valve
EP4124739A1 (fr) 2021-07-30 2023-02-01 Pratt & Whitney Canada Corp. Bloc d'orifice pour soupape de purge de compresseur
US11852073B2 (en) 2021-07-30 2023-12-26 Pratt & Whitney Canada Corp. Orifice pack for compressor bleed valve
US11639689B2 (en) 2021-09-17 2023-05-02 Pratt & Whitney Canada Corp. Intake device for gas turbine engine
US20230358171A1 (en) * 2022-05-06 2023-11-09 Pratt & Whitney Canada Corp. Apparatus for removing particulate matter from bleed gas and gas turbine engine including same
US11821363B1 (en) * 2022-05-06 2023-11-21 Pratt & Whitney Canada Corp. Apparatus for removing particulate matter from bleed gas and gas turbine engine including same

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Publication number Publication date
CA2706211A1 (fr) 2010-12-26
CA2706211C (fr) 2017-08-22
US20100326090A1 (en) 2010-12-30

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